(Department of Mechanical Engineering, Mechanical Engineering Faculty, Yildiz Technical University, Besiktas, 34349 Istanbul, Turkey)
(Department of Mechanical Engineering, Mechanical Engineering Faculty, Yildiz Technical University, Besiktas, 34349 Istanbul, Turkey)
Yıl: 2019Cilt: 7Sayı: 1ISSN: 2147-9364 / 2147-9364Sayfa Aralığı: 12 - 21İngilizce

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The present paper presents the modal analyses of a NACA 4415 airfoil profiled wing.Theoretical and numerical calculations are performed by considering the aircraft wing as a cantileverbeam. The model is created and modal analyses are performed by using commercially availablepackages of SolidWorks and Ansys, respectively. The natural frequencies and the related mode shapesare obtained. The results of theoretical calculations are compared with the numerical modal analyses.The study has a conclusion that an aircraft wing can be considered as a cantilever beam that by ignoringthe whole forces on the aircraft (except for gravity).
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